Abstract: A heat transfer arrangement for a fluid-washed body having first and second ends and a fluid-washed surface extending there-between. The arrangement includes a heat transfer member extending from the first end at least part way along the body towards the second end. A heat source is arranged in use to heat the heat transfer member in the vicinity of the first end of the body. A plurality of thermal control layers are provided on the heat transfer member, each of the layers having a different thermal conductivity and being juxtaposed so as to create a thermal conductivity profile which varies along the length of the member. The arrangement may be used for prevention of icing of an aerofoil body such as a blade, vane or the like.

Abstract: A gas turbine engine arrangement comprises a first gas turbine engine, a second gas turbine engine, a differential gearbox and an electrical generator. The differential gearbox has a first input drive, a second input drive and an output drive. The output drive of the differential gearbox is arranged to drive the electrical generator via an external, accessory, gearbox. The external, accessory, gearbox drives other accessories. The first gas turbine is arranged to drive the first input drive of the differential gearbox and the second gas turbine engine is arranged to drive the second input drive of the differential gearbox. The electrical generator and accessories are driven at a constant frequency speed/frequency.

Abstract: A drive arrangement for driving, or for being driven by, a fluid is disclosed. The drive arrangement comprises a rotatable member (40) for receiving the fluid, and having mounted thereon a plurality of drive members (56). The drive members (56) are movable between a drive position, in which the drive members can drive, or be driven by, the fluid, and a non-drive position in which the drive members (56) are substantially prevented from driving or being driven by a fluid received in the rotatable member (40).

Abstract: In order to achieve greater operational efficiency a propulsive arrangement is provided in which a relatively large number of small propulsive assemblies 9; 31, 32, 33 are provided in aircraft structures in particular the wing 7; 30. The assemblies 9; 31, 32, 33 comprise a flow path within which a compressor 39, 43, 47 is positioned to propel an air flow for propulsion. The compressors 39, 43, 47 are powered by electricity from an electricity generator 8 and possibly supplemented by solar cells or fuel cells or wing tip turbine generators 11. The assemblies 9, 31, 32, 33 are small to allow easy removal for maintenance and repair.

Abstract: An electrical power generation assembly comprising a main body having a low density to provide lift and wind driven means on its surface to generate electrical power. The main body has a part-circular, or a part-elliptical, cross section frontal region. The main body has a first distance and a second distance. The ratio of the first distance to the second distance is equal to or more than 0.5 and equal to or less than 5 according to the shape of the frontal region of the main body. The ratio of the diameter of the wind driven means to the first distance is equal to or less than 0.25.

Abstract: An indentor for contacting a bearing surface, the indentor comprising a contact surface complimentary to that of the bearing surface, wherein the indentor comprises an integral tapering portion which tapering portion defines part of the contact surface, the tapering portion at its distal edge defining an edge of contact between the contact surface and the bearing surface.

Abstract: A gas turbine engine fan blade (26) comprises a root portion (40) and an aerofoil portion (42). The aerofoil portion (42) has a leading edge (44), a trailing edge (46), a concave metal wall portion (50) extending from the leading edge (44) to the trailing edge (46) and a convex metal wall portion (52) extending from the leading edge (44) to the trailing edge (46). The aerofoil portion (42) has a hollow interior (54) and the interior (54) of the aerofoil portion (42) is at least partially filled with a vibration damping material (56). The vibration damping material (56) comprises a material having viscoelasticity for example one formed by mixing an amine terminated polymer and bisphenol a-epichlorohydrin epoxy resin.

Abstract: A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (34) comprises a generally annular, or frustoconical, cross-section casing (52). At least one corrugated sheet metal ring surrounds the casing (52) wherein the corrugations extend with axial and/or circumferential components.

Abstract: A component (24) for a gas turbine engine rotor assembly comprises a wall member (26) for at least partially bridging a space between adjacent rotor blades (18) and a root member (42) for insertion into a groove in the rotor disc (18) of the rotor assembly. The root member (42) includes bearing surfaces (46) for bearing against complementary surfaces (48) in the groove on rotation of the disc. The annulus filler (26) comprises a plurality of layers of carbon fiber reinforced plastics material, the layers being oriented substantially perpendicular to the bearing surfaces (46).

Abstract: A seal arrangement (40) between relatively movable components (42,48) includes at least one magnet (54) on a first component (48) and at least one magnet (56) on the second component (42). A clearance (55) is defined between the at least one magnet (54) on the first component (48) and the at least one magnet (56) on the second component (42). Springs (58) bias the at least one magnet (54) on the first component (48) and the at least one magnet (56) on the second component (42) towards each other. The at least one magnet (54) on the first component (42) and the at least one magnet (56) on the second component (42) are arranged to repel each other against the spring (58) to control the clearance (55).

Abstract: A fan rotor assembly (30) for a gas turbine engine (10) comprises a fan rotor (32) and a plurality of radially extending fan blades (34). Each fan blade (34) has a root (64) which is retained in a corresponding groove (54) in the periphery of the hub (54) of the fan rotor (32). Each fan blade root (64) comprises four axially spaced root portions (66, 68, 70 and 72) which locate in a corresponding number of axially spaced groove portions (56, 58, 60 and 62). The flanks (94, 98) of two of the root portions (66, 70) are arranged at an angle to the axis of the fan rotor (32) and the flanks (96, 100) of the other two root portions (68, 72) are arranged at an angle in the opposite sense. The flanks (74, 76, 78 and 80) of the groove portions (56, 58, 60 and 62) are arranged at the same angle as the flanks (94, 96, 98 and 100) of the corresponding root portions (66, 68, 70 and 72). The arrangement provides improved retention of the fan blades (34) and reduces the weight of the fan blades (34) and fan rotor (32).

Abstract: A fan for a gas turbine engine comprises a rotary disc carrying an annular array of radially extending fan blades. Each fan blade has a root portion which is radially constrained within a generally axially extending groove formed within a disc rim. The blade root comprises two portions each radially convergent toward one another with respect to the axis of rotation of the disc. The groove within the disc also comprises two base portions each being correspondingly radially convergent toward one another. Axial retention of the blade root within the groove is achieved by the centrifugal component of the blade load acting in an opposite direction to any applied axial load in the forward or rearward direction.

Abstract: A rotor for a ducted fan gas turbine engine includes a rotor disc on which a number of circumferentially spaced apart blades are mounted. Wall members are positioned to bridge the space between adjacent blades. The wall members correspond in profile with the blades adjacent thereto. A seal is mounted on a side face of each wall member and is bonded to a flexible mounting which is bonded itself to the wall member. The flexible mounting has elastic properties so as to allow the seal to deflect relative to the wall member under centrifugal loading during operation.